CN107061314A - The low-pressure compressor changed a social system using retired engine - Google Patents
The low-pressure compressor changed a social system using retired engine Download PDFInfo
- Publication number
- CN107061314A CN107061314A CN201710190544.2A CN201710190544A CN107061314A CN 107061314 A CN107061314 A CN 107061314A CN 201710190544 A CN201710190544 A CN 201710190544A CN 107061314 A CN107061314 A CN 107061314A
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- low
- pressure compressor
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- pressure
- stator
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- 230000007246 mechanism Effects 0.000 claims description 7
- 241000397426 Centroberyx lineatus Species 0.000 claims description 3
- 230000009467 reduction Effects 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000000926 separation method Methods 0.000 abstract description 4
- 230000008859 change Effects 0.000 abstract description 3
- 239000000306 component Substances 0.000 description 22
- 239000007789 gas Substances 0.000 description 12
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000008450 motivation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/34—Blade mountings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of low-pressure compressor changed a social system using retired engine, belong to gas turbine technology field, including inlet casing, low-pressure compressor stator component, low-pressure compressor rotor, newly the level work blade of low-pressure compressor the 1st 4 is designed with the basis of prototype, low-pressure compressor other structures are constant, by redesigning blade type face, on the premise of tenon shape invariance is kept, increase the angle of leaf chord length and axis, and then change the inlet air flow angle for entering stator blade below, make air-flow separation reduction, increase low-pressure compressor efficiency, and then improve low-pressure compressor overall pressure tatio, low-pressure compressor steady operation under compared with the prototype more slow-speed of revolution can be made, overall pressure tatio and efficiency on this operating point are improved simultaneously.
Description
Technical field
The invention belongs to gas turbine technology field, more particularly to a kind of low pressure changed a social system using retired engine is calmed the anger
Machine.
Background technology
With domestic gas turbine industry flourish, the deep application of gas turbine advanced design technology, high-performance,
The gas turbine of high reliability continuously emerges, and is remained high as the manufacturing cost of core component compressor.At the same time, combustion gas
Turbine product market competition increasingly sharpens, and user requires more and more higher.Gas turbine homogeneity, it is similar and meet user using will
Under conditions of asking, gas turbine price often turns into the sole indicator that can market and user receive.The combustion of existing market sale
Gas-turbine is higher due to manufacturing cost, can improve after-sale service and price for repairing, be increased burden to user.Current user has been difficult to connect
High gas turbine price is received, market receiving degree is poor.
The content of the invention
For above-mentioned technical problem, the present invention provides a kind of low-pressure compressor changed a social system using retired engine,
Its brand-new design low-pressure compressor working-blade blade type face on the basis of former retired engine low-pressure compressor, forms level pressure
Than bigger working-blade, and blade tenon structure is constant, meanwhile, low-pressure compressor other structures are constant, can improve and calm the anger
Machine stagnation pressure when efficiency, gas turbine performance can have a distinct increment relatively compared with the product of power grade.In addition, being sent out by reducing
Motivation rotating speed, it is ensured that can be in lower working condition reliably working in gas turbine.
The present invention the technical scheme used for：The low-pressure compressor changed a social system using retired engine, including inlet casing,
Low-pressure compressor stator component, low-pressure compressor rotor is characterized in that：Low-pressure compressor rotor is by the 1st to 4 level work leaf
Piece and the 1st to 4 grade of disk composition, the 1st to 4 grade of disk of low-pressure compressor rotor are correspondingly arranged at low-pressure compressor rotor the 1st respectively
Below to 4 level work blades, each working-blade lower end is provided with swallow-tail form tenon, and tenon is corresponding with low-pressure compressor rotor
The 1st to 4 grade of disk on tongue-and-groove connection.
Low-pressure compressor stator component by the 1st grade of casing of low-pressure compressor, the 1st grade of stator casing component of low-pressure compressor,
The 4th grade of the 2nd grade of stator casing component of low-pressure compressor, low-pressure compressor 3rd level stator casing component and low-pressure compressor and go out
Mouth stator casing component composition；Calmed the anger per one-level low-pressure compressor stator casing component by low-pressure compressor stator blade and low pressure
Machine stator casing is constituted.
Compared with prior art, beneficial effects of the present invention are：
1. the implementation of the present invention can effectively play increase overall pressure tatio in terms of compressor part, the work of compressor efficiency is improved
With relatively in the past directly using retired engine low-pressure compressor, both prevented causes primary motivation low pressure pressure because operating point is reduced
Mechanism of qi overall pressure tatio is reduced, the problem of efficiency is reduced, while effectively improving gas turbine functional reliability again, increases the gas turbine longevity
Life.
2. compared with newly design low-pressure compressor, performance is similar with reliable, but the present invention is because of only new development work blade,
Remaining structure directly utilizes retired engine resource, effectively reduces manufacturing cost.
Brief description of the drawings
Fig. 1 is structural representation of the invention；
Fig. 2 is H-H directions sectional view in Fig. 1；
Fig. 3 is the level work blade new construction of low-pressure compressor the 1st and prototype architectural difference schematic diagram；
Reference is as follows：1. inlet casing, 11. adjustable vanes, 2. low-pressure compressor stator components, 21. low-pressure compressors
1st grade of casing, the 1st grade of stator casing component of 22. low-pressure compressors, the 1st grade of stator blade of 221. low-pressure compressors, 222. low pressure
The 1st grade of stator casing of compressor, the 2nd grade of stator casing component of 23. low-pressure compressors, the 2nd grade of stator leaf of 231. low-pressure compressors
Piece, the 2nd grade of stator casing of 232. low-pressure compressors, 24. low-pressure compressor 3rd level stator casing components, 241. low-pressure compressors
3rd level stator blade, 242. low-pressure compressor 3rd level stator casings, the 4th grade of 25. low-pressure compressors and outlet stator casing group
Part, 3. low-pressure compressor rotors, 31. the 1st level work blades, the 1st grade of disk of 32. low-pressure compressors, 33. the 2nd level work blades,
34. the 2nd grade of disk of low-pressure compressor, 35. 3rd level working-blades, 36. low-pressure compressor 3rd level disks, 37. the 4th level work leaves
Piece, the 4th grade of disk of 38. low-pressure compressors.
Embodiment
The present invention will be described in detail with reference to the accompanying drawings and examples.
Embodiment：As shown in figure 1, the present invention is the low-pressure compressor changed a social system using retired engine, including inlet casing
1st, low-pressure compressor stator component 2, low-pressure compressor rotor 3, wherein：Low-pressure compressor rotor is by the 1st to 4 level work blade
（31,33,35,37）With the 1st to 4 grade of disk（32,34,36,38）Composition, the 1st to 4 grade of disk of low-pressure compressor rotor is corresponded to respectively
It is arranged on below the level work blade of low-pressure compressor rotor the 1st to 4, each working-blade lower end is provided with swallow-tail form tenon,
Tongue-and-groove connection on tenon the 1st to 4 grade of disk corresponding with low-pressure compressor rotor, low-pressure compressor stator component 2 is by low pressure pressure
The 1st grade of casing 21 of mechanism of qi, the 1st grade of stator casing component 22 of low-pressure compressor, the 2nd grade of stator casing component 23 of low-pressure compressor,
The 4th grade of low-pressure compressor 3rd level stator casing component 24 and low-pressure compressor and outlet stator casing component 25 are constituted, for reduction
Manufacturing cost, structure and certain retired engine low-pressure compressor structure（Hereinafter referred to as prototype）It is identical, it can use completely.
The level work blade of low-pressure compressor the 1st to 4（31,33,35,37）For new design structure, for reduction manufacturing cost and
Functional reliability is improved, low-pressure compressor disk is identical with prototype structure, so new design work blade（31,33,35,
37）Tenon structure is constant, and blade and blade height degree is identical with certain retired engine low-pressure compressor original structure, and leaf chord length is with starting
The angle α of arbor line increases along blade direction compared with prototype, and increased value is raised from blade root to blade tip.
When gas turbine works, the more former retired engine working speed of working speed declines 10%, such low-pressure compressor
The exit flow angle α of working-blades at different levels will be unable to be consistent with low-pressure compressor stator blade stagger angle β, can make
Air-flow produces larger separation at stator blade back, and air mass flow can reduce compressor overall pressure tatio and efficiency while reduction.
By changing the angle α of leaf chord length and engine axis, working-blade exit flow absolute velocity is set to occur angle
Degree change, is more nearly with stator blade stagger angle β, and stator blade is not likely to produce air-flow separation, improves low-pressure compressor
Efficiency.Simultaneously because the angle α of working-blade chord length and engine axis compared with the increased value of original structure from blade root to blade tip liter
Height, increased blade twist angle, improves low-pressure compressor overall pressure tatio.
By Pneumatic Calculation, in the state of reduction low-pressure compressor working speed 10%, keep intake air flow basic
Constant, using the low-pressure compressor after changing, overall pressure tatio can improve 14%-16%, and efficiency improves 10-12%.
By Strength co-mputation, low-pressure compressor working-blade root needs to thicken compared with original structure, because tenon structure can not
The angle α of change, low-pressure compressor working-blade root chord length and engine axis is less compared with prototype increase or is basically unchanged,
Using root of blade type face without departing from blade tenon as principle, in view of the separation of root of blade air-flow is insensitive, therefore in proof strength
On the premise of overall pressure tatio and efficiencies can receive.
The installation process of the present invention is as follows：
First, the 2nd grade of disk 34 of the 1st grade of disk 32 of the low-pressure compressor with preceding axle journal and low compressor is welded together, then by band
The low-pressure compressor 3rd level disk 36 of rear shaft neck is bolted with it, then by the 4th grade of disk 38 of low-pressure compressor and its pass through spiral shell
Tether and connect, be then respectively mounted newly-designed 1-4 level work blades（31,33,35,37）, thus form low-pressure compressor
Rotor 3.
Secondly, the inlet casing 1 with adjustable vane is placed vertically on the table, low-pressure compressor rotor 3 is vertical
Insert in inlet casing 1, axle journal before low-pressure compressor rotor is connected with inlet casing 1 by stick roller bearing, set using special
The standby relative distance for ensureing inlet casing 1 and low-pressure compressor rotor 3.
Then, the 1st grade of low-pressure compressor casing 21 is loaded on inlet casing 1 vertically, the 1st grade of stator leaf of low-pressure compressor
Piece component 221 is made up of multiple stator blades, and component is 2 semi-circular structures, by the 1st grade of stator vane assembly of low-pressure compressor
Insert, and determined by the annular groove on the 1st grade of casing 21 of low-pressure compressor between low-pressure compressor the 1st, 2 level work blades respectively
Position.
Afterwards, the 1st grade of stator casing 222 of low-pressure compressor is filled straight down, is enclosed on the 1st grade of stator leaf of low-pressure compressor
On piece component 221, positioned by the outer surface of stator vane assembly 221.Similarly, the 2nd grade of stator blade group of low-pressure compressor is filled
Part 231, the 2nd grade of stator casing 232 of low-pressure compressor, low-pressure compressor 3rd level stator vane assembly 241, low-pressure compressor the 3rd
Level stator casing 242.
Finally, the 4th grade of stator of low-pressure compressor and outlet casing component 25 are inserted vertically into low-pressure compressor 3rd level stator
In rabbet groove in casing 242, ensure centering.
Operation principle of the present invention：
The present invention new design level work blade of low pressure the 1st to 4 on the basis of former retired low-pressure compressor（31,33,35,37）,
Working speed reduction by 10% in the state of, make air from inlet casing 1 by import adjustable vane 11 axially into rear low pressure pressure
After the level work blade 31 of mechanism of qi the 1st, the absolute velocity C2 of air direction changes, and is changed to C1, speed C1 direction is right
Answer basically identical with stagger angle β in the middle part of the 1st grade of stator blade, holding does not occur along most of region of blade radial direction
Air-flow is separated.
After air is by the 1st grade of stator vane assembly 221 of low-pressure compressor, into the level work blade of low-pressure compressor the 2nd
33, similarly, by changing the angle α of the level work leaf chord length of low-pressure compressor the 2nd and engine axis, make vane inlet air-flow
It is more smooth to enter the 2nd level work blade, it is to avoid mass air flow is separated, improve compressor operating efficiency.
Air flows into the 4th grade of stator of low-pressure compressor and outlet casing 25 by the level work blade 37 of low-pressure compressor the 4th
Axially discharge afterwards.
Further, since the angle α of low-pressure compressor 1-4 level works leaf chord length and engine axis is compared with original structure increase
And increase from blade root to blade tip direction difference, make blade twist angle compared with original structure increase, pass air through after working-blade absolutely
To the increase of speed circumferential component variable quantity, single-stage compressor pressure ratio is improved, and then add low-pressure compressor overall pressure tatio.
Claims (4)
1. a kind of low-pressure compressor changed a social system using retired engine, including inlet casing, low-pressure compressor stator component, low pressure
Compressor rotor, it is characterised in that：Low-pressure compressor rotor is made up of the 1st to 4 level work blade and the 1st to 4 grade of disk, low pressure pressure
1st to 4 grade of disk of mechanism of qi rotor is correspondingly arranged at below the level work blade of low-pressure compressor rotor the 1st to 4 respectively, each work
Blade lower end is provided with the tongue-and-groove connection on swallow-tail form tenon, tenon the 1st to 4 grade of disk corresponding with low-pressure compressor rotor.
2. a kind of low-pressure compressor changed a social system using retired engine according to claim 1, it is characterised in that：Low pressure pressure
Mechanism of qi stator component is by the 1st grade of casing of low-pressure compressor, the 1st grade of stator casing component of low-pressure compressor, low-pressure compressor the 2nd
The 4th grade of level stator casing component, low-pressure compressor 3rd level stator casing component and low-pressure compressor and outlet stator casing component
Composition.
3. a kind of low-pressure compressor changed a social system using retired engine according to claim 2, it is characterised in that：Per one-level
Low-pressure compressor stator casing component includes low-pressure compressor stator blade and low-pressure compressor stator casing.
4. a kind of low-pressure compressor changed a social system using retired engine according to claim 3, it is characterised in that：Enter mechanism of qi
Casket is arranged on low-pressure compressor foremost, is installed behind inlet casing and connects low-pressure compressor behind adjustable vane, adjustable vane
Annular groove is provided with 1st grade of casing, the 1st grade of casing of low-pressure compressor, the 1st grade of casing of low-pressure compressor is vertically arranged into mechanism of qi
Inside casket, the 1st grade of stator blade of low-pressure compressor is made up of multiple stator blades, and the 1st grade of stator blade of low-pressure compressor is pacified
Fixed between low-pressure compressor the 1st, 2 level work blades, and by the annular groove on the 1st grade of casing of low-pressure compressor, low pressure
Profile For Compressor Stator component is arranged alternately with the working-blade of low-pressure compressor rotor and is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710190544.2A CN107061314A (en) | 2017-03-28 | 2017-03-28 | The low-pressure compressor changed a social system using retired engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710190544.2A CN107061314A (en) | 2017-03-28 | 2017-03-28 | The low-pressure compressor changed a social system using retired engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107061314A true CN107061314A (en) | 2017-08-18 |
Family
ID=59620222
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710190544.2A Pending CN107061314A (en) | 2017-03-28 | 2017-03-28 | The low-pressure compressor changed a social system using retired engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN107061314A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108223429A (en) * | 2017-09-30 | 2018-06-29 | 中国航发沈阳发动机研究所 | The fancase of the domain not fault wall |
| CN108953232A (en) * | 2018-07-20 | 2018-12-07 | 大连海事大学 | A kind of non-axisymmetric distribution stator blade axial-flow compressor |
| CN109458359A (en) * | 2018-12-26 | 2019-03-12 | 中国船舶重工集团公司第七0三研究所 | A kind of blade profile improving helium compressor single-stage pressure ratio |
| CN113279978A (en) * | 2021-03-23 | 2021-08-20 | 厦门大学 | Gas compressor and method for weakening sound excitation of rotor blade of gas compressor |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
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| CN203783965U (en) * | 2014-04-02 | 2014-08-20 | 清华大学 | Large-flow high-load axial-flow compressor used for 300MW F-grade heavy-duty gas turbine |
| CN104595245A (en) * | 2015-01-04 | 2015-05-06 | 南京航空航天大学 | Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
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| CN101092966A (en) * | 2007-07-23 | 2007-12-26 | 北京航空航天大学 | Compact pneumatic overall arrangement of compression system in aerial turbo fan engine |
| US20120070267A1 (en) * | 2010-09-16 | 2012-03-22 | Hitachi, Ltd. | Axial Flow Compressor, Gas Turbine System Having the Axial Flow Compressor and Method of Modifying the Axial Flow Compressor |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108223429A (en) * | 2017-09-30 | 2018-06-29 | 中国航发沈阳发动机研究所 | The fancase of the domain not fault wall |
| CN108953232A (en) * | 2018-07-20 | 2018-12-07 | 大连海事大学 | A kind of non-axisymmetric distribution stator blade axial-flow compressor |
| CN109458359A (en) * | 2018-12-26 | 2019-03-12 | 中国船舶重工集团公司第七0三研究所 | A kind of blade profile improving helium compressor single-stage pressure ratio |
| CN113279978A (en) * | 2021-03-23 | 2021-08-20 | 厦门大学 | Gas compressor and method for weakening sound excitation of rotor blade of gas compressor |
| CN113279978B (en) * | 2021-03-23 | 2024-01-26 | 厦门大学 | Compressor and method for weakening acoustic excitation of compressor rotor blade |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20200306 Address after: Room 223, building 2, No. 1, Shuanghu North Road, Xiang'an District, Xiamen City, Fujian Province Applicant after: Xiamen zhongguanneng Gas Turbine Technology Co.,Ltd. Address before: 110043 Liaoning Province, Shenyang City District Li neighbors Road No. 11 North Lane Applicant before: Shenyang Guanneng Gas Turbine Technology Co.,Ltd. |
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Application publication date: 20170818 |
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